Exact solution for buckling of axially-compressed cylindrical panels with frames attached to the circular edges

Soares, P. T. M. L.; Santana, R. C.; Lucena Neto, E.; Monteiro, F. A. C.; Souza Neto, A. F.; Queiroz, P. I. B.

doi:10.1590/1679-78255903

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THEMATIC SECTION: SOLID MECHANICS IN BRAZIL 2019 • Lat. Am. j. solids struct. 17 (08) • 2020 • https://doi.org/10.1590/1679-78255903 copy

Exact solution for buckling of axially-compressed cylindrical panels with frames attached to the circular edges

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Abstract

This paper presents an exact solution for the boundary-value problem which describes the linear buckling of axially-compressed cylindrical panels with frames attached to the circular edges. The boundary conditions differ from the classical simply supported ones, often assumed for design purposes, in the sense that the torsion resisted by the frames are also taken into account. The quality of the results reported herein may be valuable benchmark data.

Keywords:
Cylindrical panel; Buckling; Exact solution; Frame

Graphical Abstract

( $J_{f}, Γ_{f}, I_{f}$ )	$b / a$		$R / h$
( $J_{f}, Γ_{f}, I_{f}$ )	$b / a$	500	1000	1500
(0,0,0)	0.2	1.00171 (1,a,I)^a	1.01779 (1,s,IV)	1.18156 (1,s,IV)
	0.4	1.00152 (1,a,I)	1.00256 (1,a,I)	1.00122 (1,s,I)
	0.6	1.00004 (2,a,I)	1.00102 (1,s,I)	1.00004 (1,s,I)
	0.8	1.00000 (5,a,I)^b	1.00012 (3,a,I)	1.00026 (3,a,III)
	1.0	1.00018 (3,a,I)	1.00000 (1,s,I)^b	1.00017 (3,a,I)
	1.2	1.00004 (4,a,I)	1.00001 (1,s,I)	1.00004 (2,s,I)
	1.4	1.00000 (9,a,III)^b	1.00001 (6,s,I)	1.00018 (4,a,I)
(96,36370,853)	0.2	1.00618 (1,a,I)	1.02644 (1,a,III)	1.20792 (1,s,III)
	0.4	1.00618 (2,a,I)	1.01775 (1,a,I)	1.00402 (1,s,I)
	0.6	1.00430 (4,a,III)	1.01338 (2,a,I)	1.00295 (2,a,I)
	0.8	1.00047 (5,s,I)	1.00355 (3,a,I)	1.00363 (3,s,III)
	1.0	1.00085 (6,a,I)	1.00578 (4,s,I)	1.01160 (3,a,I)
	1.2	1.00230 (7,a,I)	1.00288 (5,s,I)	1.00295 (4,a,I)
	1.4	1.00050 (9,a,III)	1.00170 (6,s,I)	1.00085 (5,s,I)

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